Strapdown heading sensors and systems, and methods of calibrating and compensating the same

ABSTRACT

A strapdown heading sensor includes an elongated housing and a compass module at least partially positioned within an inner cavity of the elongated housing. The compass module is cantilevered within the inner cavity of the elongated housing.

RELATED APPLICATIONS

This application claims the benefit of U.S. Provisional Application No. 61/398,917, filed Jul. 2, 2010, the content of which is incorporated herein by reference in its entirety.

TECHNICAL FIELD

The present application generally relates to heading sensors, and more particularly, to strapdown heading sensors and systems, and methods of calibrating and compensating strapdown heading sensors and systems.

BACKGROUND

Heading sensors have a variety of uses. For example, heading sensors may be employed in vehicles, projectiles, towed arrays and/or other devices requiring heading information. However, solid-state electronic devices included in heading sensors can be affected by environmental conditions and component variations, which can limit the accuracy of the heading sensors. In addition, on-axis errors, intra-axis errors and/or intra-sensor errors may further limit the accuracy of the heading sensors.

SUMMARY

Embodiments of the present inventive concepts are directed to strapdown heading sensors and systems, and methods of calibrating and compensating strapdown heading sensors and systems.

In one aspect, a strapdown heading sensor, comprises: an elongated housing, and a compass module at least partially positioned within an inner cavity of the elongated housing. The compass module is cantilevered within the inner cavity of the elongated housing.

In some embodiments, the compass module is coupled to a surface of the inner cavity of the elongated housing.

In some embodiments, a proximal end of the compass module is coupled to a proximal end of the elongated housing, and wherein a distal end of the compass module is suspended within a central region of the inner cavity of the elongated housing.

In some embodiments, an end-cap of the compass module is press fit within a proximal end of the elongated housing.

In some embodiments, an o-ring is compressed between the end-cap of the compass module and the surface of the inner cavity of the elongated housing.

In some embodiments, the compass module includes a compass package secured between a first compass module member and a second compass module member.

In some embodiments, the first and second compass module members are constructed and arranged to secure the compass package within the elongated housing.

In some embodiments, the compass package includes a fluxgate magnetometer system and at least one accelerometer.

In some embodiments, the fluxgate magnetometer system and the at least one accelerometer are coupled to a printed circuit board of the compass package.

In some embodiments, a fluxgate magnetometer of the fluxgate magnetometer system is coupled to a first printed circuit board of the compass package and the at least one accelerometer is coupled to a second printed circuit board of the compass package.

In some embodiments, the fluxgate magnetometer system includes a tri-axial fluxgate magnetometer system.

In some embodiments, the fluxgate magnetometer system includes first through third uni-axial fluxgate magnetometers.

In some embodiments, the first through third uni-axial fluxgate magnetometers are transversely coupled to the compass package with respect to one another.

In some embodiments, the first uni-axial fluxgate magnetometer is coupled to a first printed circuit board of the compass package and the second and third uni-axial fluxgate magnetometers are coupled to a second printed circuit board of the compass package.

In some embodiments, the at least one accelerometer is coupled to the second printed circuit board.

In some embodiments, the at least one accelerometer includes a pair of accelerometers, and wherein a first accelerometer of the pair of accelerometers is coupled to a first side of the second printed circuit board, and wherein a second accelerometer of the pair of accelerometers is coupled to a second side, opposite the first side, of the second printed circuit board.

In some embodiments, the at least one accelerometer includes a uni-axial accelerometer.

In some embodiments, the at least one accelerometer includes first through third uni-axial accelerometers, and wherein the first uni-axial accelerometer is constructed and arranged to detect a first acceleration vector, the second uni-axial accelerometer is constructed and arranged to detect a second acceleration vector transverse to the first acceleration vector, and the third uni-axial accelerometer is constructed and arranged to detect a third acceleration vector transverse to the first and second acceleration vectors.

In some embodiments, the at least one accelerometer includes a bi-axial accelerometer.

In some embodiments, the at least one accelerometer includes first and second bi-axial accelerometers, wherein the first bi-axial accelerometer is constructed and arranged to detect first and second acceleration vectors, the first acceleration vector being transverse to the second acceleration vector, and wherein the second bi-axial accelerometer is constructed and arranged to detect third and fourth acceleration vectors, the third acceleration vector being transverse to the fourth acceleration vector.

In some embodiments, the second and third acceleration vectors are collinear.

In some embodiments, the second acceleration vector is transverse to the third acceleration vector.

In some embodiments, the at least one accelerometer includes a tri-axial accelerometer.

In some embodiments, the at least one accelerometer includes a micro electromechanical systems (MEMS) accelerometer device.

In some embodiments, the at least one accelerometer includes a pair of accelerometers, and wherein a first accelerometer of the pair of accelerometers is coupled to a first side of the compass package, and wherein a second accelerometer of the pair of accelerometers is coupled to a second side, opposite the first side, of the compass package.

In some embodiments, the at least one accelerometer includes at least two pairs of accelerometers.

In some embodiments, the second compass module member is coupled to the first compass module member via one or more fasteners.

In some embodiments, the first compass module member is integrally joined with an end-cap of the compass module.

In some embodiments, the strapdown heading sensor further comprises a processing module positioned within the inner cavity of the cylindrical housing.

In some embodiments, the processing module is structurally isolated from the compass module.

In some embodiments, the strapdown heading sensor further comprises a flexible cable, the flexible cable electrically coupling the compass module to the processing module.

In some embodiments, the processing module is constructed and arranged to determine at least one of pitch, roll and yaw of the elongated housing based in part on data signals received from the compass module.

In some embodiments, the elongated housing is coupled to a towed array of a submarine or surface ship.

In some embodiments, the strapdown heading sensor is configured to determine an attitude of a portion of the towed array.

In some embodiments, the elongated housing is cylindrically shaped.

In another aspect, a strapdown heading sensor, comprises an elongated housing, and a compass module positioned within an inner cavity of the elongated housing. The compass module is passively isolated from shock or vibrations induced on an outer surface of the elongated housing.

In some embodiments, the elongated housing includes a closed housing, and wherein the strapdown heading sensor further comprises an end-cap constructed and arranged to close a single opening of closed housing.

In some embodiments, the elongated housing includes an opened housing, and wherein the strapdown heading sensor further comprises a first end-cap constructed and arranged to close a first opening of the opened housing and a second end-cap constructed and arranged to close a second opening of the opened housing.

In some embodiments, the strapdown heading sensor further comprises a damper positioned between the compass module and a surface of the inner cavity of the elongated housing.

In some embodiments, the damper includes a first damper positioned about a proximal end of the compass module and a second damper positioned about a distal end of the compass module.

In some embodiments, the damper includes an o-ring.

In some embodiments, the damper includes a bumper.

In some embodiments, the compass module includes a compass package, the compass package including a fluxgate magnetometer system and at least one accelerometer.

In some embodiments, the fluxgate magnetometer system and the at least one accelerometer are coupled to a printed circuit board of the compass module.

In some embodiments, a first accelerometer of the at least one accelerometer is coupled to a first side of the printed circuit board, and wherein a second accelerometer of the at least one accelerometer is coupled to a second side, opposite the first side, of the printed circuit board.

In some embodiments, the fluxgate magnetometer system includes first through third uni-axial fluxgate magnetometers.

In some embodiments, the compass module includes a processing package, the processing package including a control system.

In some embodiments, the processing package is coupled to the printed circuit board of the compass module.

In some embodiments, the processing package is constructed and arranged to determine at least one of pitch, roll and yaw of the elongated housing based in part on data signals received from the compass package.

In some embodiments, the elongated housing is coupled to a towed array of a submarine or surface ship.

In some embodiments, the strapdown heading sensor is configured to determine an attitude of a portion of the towed array.

In another aspect, a method of calibrating a strapdown heading sensor, comprises: compensating raw sensor data generated by sensors of an uncalibrated strapdown heading sensor to compensate for errors in an instrument frame of the strapdown heading sensor; providing the strapdown heading sensor in a target apparatus; and after providing the strapdown heading sensor in the target apparatus, compensating output data of the strapdown heading sensor to compensate for errors in an apparatus frame of the target apparatus relative to the instrument frame of the strapdown heading sensor.

In some embodiments, the errors in the instrument frame of the strapdown heading sensor include at least one of: a misalignment of the sensors mounted within a housing of the strapdown heading sensor, an intra-sensor nonorthogonal error, an inter-sensor nonorthogonal error, a gain error, a bias error and hard/soft iron errors of the sensors of the strapdown heading sensor.

In some embodiments, the errors are temperature affected.

In some embodiments, the errors in the apparatus frame of the strapdown heading sensor include at least one of: a misalignment of the sensors mounted within a housing of the strapdown heading sensor, a misalignment of the strapdown heading sensor mounted within the target apparatus, an intra-sensor nonorthogonal error, an inter-sensor nonorthogonal error, a gain error, a bias error and hard/soft iron errors of the sensors of the strapdown heading sensor.

In some embodiments, the errors are temperature affected.

In some embodiments, compensating raw sensor data generated by sensors of an uncalibrated strapdown heading sensor includes: applying test conditions to the uncalibrated strapdown sensor; computing compensation coefficients based on raw sensor data generated by the uncalibrated strapdown sensor and reference data determined from a known reference source; and compensating the raw sensor data so that compensated sensor data generated by the strapdown heading sensor corresponds to a physical orientation of the strapdown heading sensor.

In some embodiments, the known reference source is calculated based on a geographical location of the strapdown heading sensor.

In some embodiments, the known reference source is calculated based on a position of the strapdown heading sensor relative to the Earth's magnetic field.

In some embodiments, the known reference source is generated by a reference sensor.

In some embodiments, applying test conditions to the uncalibrated strapdown sensor includes at least one of: varying a temperature of the uncalibrated strapdown sensor, varying an orientation of the uncalibrated strapdown sensor, varying magnetic fields applied to the uncalibrated strapdown sensor and altering a position of the uncalibrated strapdown heading sensor so as to affect a gravitational field applied to the uncalibrated strapdown sensor.

In some embodiments, the method further comprises: converting the compensated sensor data in the instrument frame of the strapdown heading sensor to compensated sensor data in the Earth's frame relative to the strapdown heading sensor; and outputting compensated sensor data in the Earth's frame relative to the strapdown heading sensor.

In some embodiments, providing the strapdown heading sensor in a target apparatus introduces the errors in the apparatus frame relative to the strapdown heading sensor.

In some embodiments, compensating output data of the strapdown heading sensor includes: applying test conditions to the strapdown sensor provided in the target apparatus; computing compensation coefficients based on sensor data generated by the strapdown sensor and reference data determined from a known reference source; and compensating the sensor data so that compensated sensor data generated by the strapdown heading sensor corresponds to a physical orientation of the target apparatus.

In some embodiments, applying test conditions to the strapdown sensor provided in the target apparatus includes at least one of: varying a temperature of the strapdown sensor, varying an orientation of the uncalibrated strapdown sensor, varying magnetic fields applied to the uncalibrated strapdown sensor and altering a position of the uncalibrated strapdown heading sensor so as to affect a gravitational field applied to the uncalibrated strapdown sensor.

In some embodiments, the known reference source is calculated based on a geographical location of the strapdown heading sensor.

In some embodiments, the known reference source is calculated based on a position of the strapdown heading sensor relative to the Earth's magnetic field.

In some embodiments, the known reference source is generated by a reference sensor.

BRIEF DESCRIPTION OF THE DRAWINGS

The foregoing and other objects, features and advantages of embodiments of the present inventive concepts will be apparent from the more particular description of preferred embodiments, as illustrated in the accompanying drawings in which like reference characters refer to the same elements throughout the different views. The drawings are not necessarily to scale, emphasis instead being placed upon illustrating the principles of the preferred embodiments.

FIG. 1 is a perspective view of a strapdown heading sensor, in accordance with embodiments of the present inventive concepts.

FIG. 2 is an internal perspective view of the strapdown heading sensor shown in FIG. 1, in accordance with embodiments of the present inventive concepts.

FIG. 3 is an exploded perspective view of the strapdown heading sensor shown in FIG. 1, in accordance with embodiments of the present inventive concepts.

FIG. 4 is a cross-sectional view of the strapdown heading sensor shown in FIG. 1, in accordance with embodiments of the present inventive concepts.

FIG. 5 is a perspective view of another strapdown heading sensor, in accordance with embodiments of the present inventive concepts.

FIG. 6 is a block diagram of a strapdown heading sensor, in accordance with embodiments of the present inventive concepts.

FIGS. 7-9 are flow diagrams of a method of calibrating a strapdown heading sensor, in accordance with embodiments of the present inventive concepts.

FIG. 10 illustrates a towed array, in accordance with embodiments of the present inventive concepts.

DETAILED DESCRIPTION OF EMBODIMENTS

The terminology used herein is for the purpose of describing particular embodiments and is not intended to be limiting of the inventive concepts. As used herein, the singular forms “a,” “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises,” “comprising,” “includes” and/or “including,” when used herein, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.

It will be understood that, although the terms first, second, third etc. may be used herein to describe various limitations, elements, components, regions, layers and/or sections, these limitations, elements, components, regions, layers and/or sections should not be limited by these terms. These terms are only used to distinguish one limitation, element, component, region, layer or section from another limitation, element, component, region, layer or section. Thus, a first limitation, element, component, region, layer or section discussed below could be termed a second limitation, element, component, region, layer or section without departing from the teachings of the present application.

It will be further understood that when an element is referred to as being “on” or “connected” or “coupled” to another element, it can be directly on or above, or connected or coupled to, the other element or intervening elements can be present. In contrast, when an element is referred to as being “directly on” or “directly connected” or “directly coupled” to another element, there are no intervening elements present. Other words used to describe the relationship between elements should be interpreted in a like fashion (e.g., “between” versus “directly between,” “adjacent” versus “directly adjacent,” etc.). When an element is referred to herein as being “over” another element, it can be over or under the other element, and either directly coupled to the other element, or intervening elements may be present, or the elements may be spaced apart by a void or gap.

FIG. 1 is a perspective view of a strapdown heading sensor, in accordance with embodiments of the present inventive concepts. A strapdown heading sensor 100 comprises an elongated housing 105 having a proximal end 105 p, a central region 105 c and a distal end 105 d. The elongated housing 105 may be cylindrical or ellipsoidal in shape. In some embodiments, the elongated housing 105 may include a formed, milled or extruded tube. The elongated housing 105 may include a metal material, a ceramic material or a plastic material. In some embodiments the elongated hosing 105 may comprise aluminum, stainless steel, titanium, a non-magnetic material, or a combination thereof.

Further, the elongated housing 105 may include an opened housing or a closed housing. For example, the strapdown heading sensor 100 shown in FIGS. 1-4 includes an opened elongated housing 105 having a first opening at its proximal end 105 p and a second opening at its distal end 150 d. Alternatively, the strapdown heading sensor 100 shown in FIG. 5 includes a closed elongated housing 105 having a single opening at its proximal end 105 p.

Referring to FIG. 1, the strapdown heading sensor 100 may further comprise first and second end caps 110, 120, which may be coupled to and/or press fit within the ends of the elongated housing 105. For example, the first end cap 110 may be coupled to the proximal end 105 p of the elongated housing 105, and the second end cap 120 may be coupled to the distal end 105 d of the elongated housing 105. One or more fasteners 122, such as screws, rivets or bolts, may be provided to securely fasten the first and second end caps 110, 120 to the elongated housing 105. However, alternatively or additionally, a glue, epoxy or sealant may be provided to couple the first and second end caps 110, 120 to the elongated housing 105. In some embodiments, the first and second end caps 110, 120 may be shrink fit within the ends of the elongated housing.

The first end cap 110 may include an alignment notch 111 or other type of marking that indicates the instrument frame of the strapdown heading sensor 100.

FIG. 2 is an internal perspective view of the strapdown heading sensor shown in FIG. 1, FIG. 3 is an exploded perspective view of the strapdown heading sensor shown in FIG. 1, and FIG. 4 is a cross-sectional view of the strapdown heading sensor shown in FIG. 1, in accordance with embodiments of the present inventive concepts. The strapdown heading sensor 100 comprises a compass module 130 and a processing module 140, each of which may be secured within an inner cavity of the elongated housing 105. The compass module 130 is configured to generate and output data signals corresponding to a strength and/or direction of the Earth's magnetic field, and may further generate and output data signals corresponding to a strength and/or direction of gravitational acceleration of the strapdown heading sensor 100. The processing module 140 is configured to determine at least one of pitch, roll and yaw of the strapdown heading sensor 100 based in part on the data signals output from the compass module 130. Data signals corresponding to pitch, roll and/or yaw may be provided to other systems and devices via an input/output (I/O) harness 160, which may include wiring 161 and a connector 162.

In the embodiment shown in FIGS. 1-4, the compass module 130 and the processing module 140 are structurally isolated from one another when mounted within the elongated housing 105. In this manner, solid state sensors (e.g., magnetometers and/or accelerometers) of the compass module 130 may be isolated from unwanted shocks and vibrations induced on the processing module 140.

In addition, the compass module 130 may be cantilevered within the inner cavity of the elongated housing 105 so that the solid state sensors of the compass module 130 stay in relative alignment with the alignment notch 111. As described below with reference to FIGS. 7-9, the strapdown heading sensor 100 may be calibrated to the instrument frame of the strapdown heading sensor, which may be indicated by the alignment notch 111. By cantilevering the compass module 130 within the inner cavity of the elongated housing 105, the calibration of the strapdown heading sensor relative to the alignment notch 111 may be maintained even during flexing or bending of the elongated housing 105. That is, a clearance space between the inner cavity walls of the elongated housing 105 and the cantilevered compass module 130 will allow the elongated housing 105 to flex and/or bend without disturbing the alignment of the compass module.

For example, a proximal end 130 p of the compass module 130 may be coupled to a proximal end 105 p of the elongated housing 105 so that a central region 130 c and a distal end 130 d of the compass module 130 may be suspended within a central region 105 c of the inner cavity of the elongated housing 105. An o-ring 112 or other damper may be compressed between the first end-cap 110 of the compass module 130 and a surface of the inner cavity of the elongated housing 105 so as to seal the proximal end 105 of the elongated housing 105. In some embodiments, an o-ring and/or other damper may be provided to reduce shocks and vibrations induced on the compass module 130.

As described above, the first end-cap 110 of the compass module 130 may be press fit within the proximal end 105 p of the elongated housing 105. In addition, the first end cap 110 may be integrally joined with a first member 131 of the compass module 130; however, in other embodiments the first end cap 110 may be a discrete element that may be coupled to the first member 131 of the compass module 130.

The compass module 130 includes a compass package 133 having solid-state sensors mounted thereon, and can be secured between first and second members 131, 132 of the compass module 130. The first and second members 131, 132 may be constructed and arranged to secure the compass package 133 within the elongated housing 105, and may further increase the structural integrity of the compass package 133. As such, the first and second members 131, 132 may prevent the compass package from warping due to external or internal temperature fluctuations. The first and second members 131, 132 may be secured together via fasteners 137, 138, such as screws, rivets or bolts. However, alternatively or additionally, a glue, epoxy or sealant may be provided to secure the first and second members 131, 132 together. The first and second members 131, 132 may comprise aluminum or other structurally rigid material.

The compass package 133 includes a fluxgate magnetometer system 201 and at least one accelerometer 205 a-b, 206 a-b, 207 a-b, 208 a-b. The fluxgate magnetometer system 201 and the at least one accelerometer 205 a-b, 206 a-b, 207 a-b, 208 a-b may be coupled to a substrate 134, such as a printed circuit board, interconnect structure or dielectric layer of the compass package 133. In some embodiments, the fluxgate magnetometer system 201 and the at least one accelerometer 205 a-b, 206 a-b, 207 a-b, 208 a-b are coupled to a single substrate 134; however, in other embodiments the fluxgate magnetometer system 201 and the at least one accelerometer 205 a-b, 206 a-b, 207 a-b, 208 a-b are coupled to multiple substrates 134, 135. For example, in the embodiment shown in FIGS. 2-4, a first fluxgate magnetometer 202 of the fluxgate magnetometer system 201 is coupled to a first substrate 135 of the compass package 133, and second and third fluxgate magnetometers 203, 204 of the fluxgate magnetometer system 201 are coupled to a second substrate 134 of the compass package 133. In some embodiments, the first substrate 135 is directly coupled to the second substrate 134; however, in other embodiments the first substrate 135 is coupled to the second member 132 of the compass module 130 via one or more fasteners 136.

The fluxgate magnetometer system 201 shown in FIG. 4 includes a tri-axial fluxgate magnetometer system including first through third uni-axial fluxgate magnetometers 202, 203, 204. The first through third uni-axial fluxgate magnetometers 202, 203, 204 are transversely coupled to the compass package 133 with respect to one another so as to detect three (3) different magnetic field vectors. However, in other embodiments the tri-axial fluxgate magnetometer system may include a single tri-axial fluxgate magnetometer device.

The compass package 133 may include one or more accelerometers or pairs of accelerometers 205 a-b, 206 a-b, 207 a-b, 208 a-b, which may include any number or combination of uni-axial, bi-axial or tri-axial accelerometers. In the embodiment shown in FIG. 4, a first accelerometer 205 a of a pair of accelerometers 205 a-b is coupled to a first side of the substrate 134 and a second accelerometer 205 b of the pair of accelerometers 205 a-b is coupled to a second side, opposite the first side, of the substrate 134. Second, third and fourth pairs of accelerometers 206 a-b, 207 a-b, 208 a-b are shown coupled to the substrate 134 in similar fashion. However, in other embodiments the one or more accelerometers or pairs of accelerometers 205 a-b, 206 a-b, 207 a-b, 208 a-b may be coupled to a single side of the substrate 134.

In some embodiments, the compass package 133 may include one or more uni-axial accelerometers. For example, the compass package 133 may include first through third uni-axial accelerometers. The first uni-axial accelerometer may be constructed and arranged to detect a first acceleration vector. The second uni-axial accelerometer may be constructed and arranged to detect a second acceleration vector transverse to the first acceleration vector, and the third uni-axial accelerometer may be constructed and arranged to detect a third acceleration vector transverse to the first and second acceleration vector. The first through third uni-axial accelerometers may be coupled to a single side of the substrate 134. Alternatively, the first through third uni-axial accelerometers may be coupled to first through third substrates, respectively.

Alternatively or additionally, the compass package 133 may include one or more bi-axial accelerometers. For example, the compass package 133 may include first and second bi-axial accelerometers. The first bi-axial accelerometer may be constructed and arranged to detect first and second acceleration vectors. The first acceleration vector may be transverse to the second acceleration vector. The second bi-axial accelerometer may be constructed and arranged to detect the third and fourth acceleration vectors. The third acceleration vector may be transverse to the fourth acceleration vector. In some embodiments, the second and third acceleration vectors may be collinear; however, in other embodiments, the second acceleration vector may be transverse to the third acceleration vector. Alternatively or additionally, the compass package 133 may include one or more tri-axial accelerometers.

Regardless of the type of accelerometer, each accelerometer of the strapdown heading sensor may be coupled to a single substrate 134 or a plurality of individual substrates, which may be secured between the members 131, 132 of the compass module 130.

The strapdown heading sensor 100 further comprises a flexible cable 150. The flexible cable 150 electrically couples the compass module 130 to the processing module 140, and may further help to reduce the transfer of mechanical stresses and/or vibrations from the processing module 140 to the compass module 130.

The processing module 140 may include a single processing package, or alternatively, the processing module 140 may include first and second processing packages 144, 145. The single processing package or the first and second processing packages 144, 145 may be suspended within the interior of the elongated housing by first and second suspension caps 141, 142.

FIG. 5 is a perspective view of another strapdown heading sensor, in accordance with embodiments of the present inventive concepts. The strapdown heading sensor 100 shown in FIG. 5 may include any of the devices, systems, elements or features of the strapdown heading sensor shown and described above with reference to FIGS. 1-4.

As described above, the strapdown heading sensor 100 shown in FIG. 5 includes a closed elongated housing 105 having a single opening at its proximal end 105 p, which can be closed by an end cap 120. A combined compass and processing module 300 may be positioned within the inner cavity of the elongated housing 105, and may further be sealed and/or secured therein. For example, the combined compass and processing module 300 may be suspended within the inner cavity of the elongated housing 105. Although the combined compass and processing module 300 is shown positioned within the inner cavity of a closed housing, the combined compass and processing module 300 may alternatively be positioned within an open housing, such as the open housing shown in FIGS. 1-4.

The strapdown heading sensor 100 is constructed and arranged to passively isolate the combined compass and processing module 300 from vibrations induced on an outer surface of the elongated housing 105. To achieve this result, the combined compass and processing module 300 may be suspended within the inner cavity of the elongated housing 105 by one or more dampers, such as an o-ring 312, 313 and/or bumper 310, 311. For example, in the embodiment shown in FIG. 5, first and second o-rings 312, 313 are provided at proximal and distal ends 300 p, 300 d of the combined compass and processing module 300 so as to reduce the transfer of vibrations from the elongated housing 105 to the combined compass and processing module 300. In addition, first and second bumpers 310, 311 may be provided at ends of the combined compass and processing module 300 to further reduce unwanted vibrations.

The combined compass and processing module 300 includes a compass package and a processing package. The compass package may include a fluxgate magnetometer system and at least one accelerometer or pair of accelerometers, and the processing package may include control circuitry configured to determine at least one of pitch, roll and yaw of the strapdown heading sensor 100 based in part on the data signals output from the compass package.

The processing package and the compass package of the combined compass and processing module 300 may be integrated on a single substrate; however, as described above with reference to FIGS. 1-4, the processing package and the compass package may be separate substrates electrically coupled by a cable.

FIG. 6 is a block diagram of a strapdown heading sensor, in accordance with embodiments of the present inventive concepts. The strapdown heading sensors 100 shown and described above with reference to FIGS. 1-5 comprise a control system architecture 200, which will now be described in further detail.

As described above, the compass module 130 or the compass package of the combined compass and processing module 300 may be configured to generate and output data signals DS 1 corresponding to a strength and/or direction of the Earth's magnetic field, and may further generate and output data signals DS 2 corresponding to a strength and/or direction of gravitational acceleration of the strapdown heading sensor 100. The processing module 140 or the processing package of the combined compass and processing module 300 may be configured to determine at least one of pitch, roll and yaw of the strapdown heading sensor 100 based in part on the data signals DS 1, DS 2 output from the compass module 130 or the compass package of the combined compass and processing module 300. Data signals DS 3 corresponding to pitch, roll and/or yaw may be provided to other systems and devices of a target apparatus via an input/output (I/O) connection 220.

The control system architecture 200 includes a power supply 210, which is configured to convert and/or condition an external current supply PWEX to one or more internal current supplies PW1, PW2. For example, in the embodiment shown in FIG. 6, the power supply 210 supplies a first current supply PW1 to the compass module 130 or the compass package of the combined compass and processing module 300, and further supplies a second current supply PW2 to the processing module 140 or the processing package of the combined compass and processing module 300.

The compass module 130 or the compass package of the combined compass and processing module 300 includes a magnetometer system 201, which may include one or more fluxgate magnetometers, and one or more accelerometers or pairs of accelerometers 205-208. In response to drive signals DR1, DR2 generated by magnetometer drive electronics 216 and accelerometer drive electronics 217 of the processing module 140 or the processing package of the combined compass and processing module 300, the magnetometer system 201 and the one or more accelerometers or pairs of accelerometers 205-208 may generate the output data signals DS1, DS2.

The processing module 140 or the processing package of the combined compass and processing module 300 may include a microprocessing system 215, magnetometer drive electronics 216, accelerometer drive electronics 217 and an analog-to-digital (A/D) converter 218. The A/D converter 318 may receive and process the output data signals DS1, DS2 from the magnetometer system 201 and the one or more accelerometers or pairs of accelerometers 205-208, and may transmit digitized signals DSD1, DSD2 to the microprocessing system 215. The microprocessing system 215 may be configured to control the operation of the strapdown heading sensor 100 so as to generate the data signals DS3, and may further be configured to perform various compensating and calibration routines.

The methods described herein can be implemented by the sensors 100 and/or the control system architectures 200 executing a unique set of instructions stored in memory of the microprocessing system 215. As will be appreciated by those skilled in the art, a unique set of instructions can be implemented or embodied in executable code, such as, software, firmware, machine code or a combination thereof. As such, the unique set of instructions stored in memory transforms the systems and/or architectures into particular, special purpose systems and architectures that can operate, for example, according to the following exemplary flow diagrams.

FIGS. 7-9 are flow diagrams of a method of calibrating a strapdown heading sensor, in accordance with embodiments of the present inventive concepts. A strapdown heading sensor 100 may be configured to perform a method of calibration 400 in order to compensate for environmental conditions (e.g., temperature fluctuations) and sensor errors. In addition, the method of calibration 400 may be performed to compensate for a misalignment and/or additional hard/soft iron errors of a strapdown heading sensor 100 mounted within a target apparatus.

TABLE 1 Accelerometers Magnetometers On-axis Errors Bias/Offset Bias/Offset Scale/Gain Scale/Gain Hard Iron Intra-axis Errors Nonorthogonality Nonorthogonality Soft Iron Intra-sensor Errors Misalignment Misalignment

Table 1 illustrates several types of errors that can affect accelerometer and magnetometer measurements. In addition to temperature fluctuations, the above sensor errors can alter the accuracy of a strapdown heading sensor. To compensate for these errors and others, the method of calibration 400 includes a factory calibration routine 415 and a platform calibration routine 445.

Referring to FIG. 7, during the factory calibration routine 415, an uncalibrated strapdown heading sensor is provided 410, and raw sensor data generated by sensors of the uncalibrated strapdown heading sensor are compensated for errors in the instrument frame of the strapdown heading sensor 420. As a result, a factory calibrated strapdown heading sensor 430 is provided, which is configured to generate data signals (e.g., data signals DS3 of FIG. 6) that are calibrated to the instrument frame of the strapdown heading sensor. As described above, the instrument frame of the strapdown heading sensor may be indicated by an alignment notch (e.g., alignment notch 111 of FIGS. 1-5) in the housing of the strapdown heading sensor.

Following the factory calibration routine 415, a platform calibration routine 445 may be performed. Prior to or at the start of the platform calibration routine 445, the strapdown heading sensor is installed in or mounted to a target apparatus. For example, the strapdown heading sensor may be installed in a towed array 502 (e.g., towed array of FIG. 10) or other device. After installation of the strapdown heading sensor in the target apparatus, the output data of the strapdown heading sensor 100 is compensated for errors in the apparatus frame of the target apparatus relative to the instrument frame of the strapdown heading sensor. As a result, a platform calibrated strapdown heading sensor 460 is provided. A platform calibrated strapdown heading sensor is configured to generate data signals (e.g., data signals DS3 of FIG. 6) that are recalibrated to the apparatus frame of the target apparatus. In this manner, alignment errors and/or additional hard/soft iron errors introduced during the installation or mounting of the strapdown heading sensor can be compensated.

The errors in the instrument frame and/or the apparatus frame of the strapdown heading sensor may include: a misalignment of the sensors mounted within a housing of the strapdown heading sensor, a misalignment of the strapdown heading sensor mounted within the target apparatus, an intra-sensor nonorthogonal error, an inter-sensor nonorthogonal error, a gain error, a bias error and hard/soft iron errors of the sensors of the strapdown heading sensor. These errors may further be affected by other environmental variables, such as temperature.

Various systems and methods of determining compensation coefficients and compensating sensor outputs are known in the art, and may be used in whole or in part with the method of calibration 400 described herein. U.S. Pat. No. 4,698,912, issued on Oct. 13, 1987 and U.S. Pat. No. 7,555,398, issued on Jun. 30, 2009, are each incorporated herein by reference in their entirety. In addition, the journal article titled “Calibration of Strapdown Magnetometers in Magnetic Field Domain”, by Demoz Gebre-Egziabher, et al., printed in the Journal of Aerospace Engineering, Vol. 19, No. 2, April 2006, pp. 87-102, is incorporated herein by reference in its entirety. Further, the article titled “Numerical calibration for 3-axis accelerometers and magnetometers”, by F. Camps, et al., printed in the Electro/Information Technology, 2009. eit '09. IEEE International Conference, 7-9 Jun. 2009, Print ISBN: 978-1-4244-3354-4, is incorporated herein by reference in its entirety.

Referring to FIG. 8, a factory calibrated strapdown heading sensor is provided as a result of the factory calibration routine 415. During the factory calibration routine 415, accelerometers and magnetometers of the uncalibrated strapdown heading sensor are compensated so that sensor data generated by the strapdown heading sensor corresponds to a physical orientation of the strapdown heading sensor.

To compensate the raw sensor data generated by the sensors 411, 412 of the uncalibrated strapdown heading sensor, test conditions TC1, TC2 are applied to the sensors 411, 412 of the uncalibrated strapdown heading sensor, and compensation coefficients are computed 421, 422 based on the raw sensor data generated by the sensors 411, 412 of the uncalibrated strapdown heading sensor and reference data determined from a known reference source. As a result, calibrated accelerometers and magnetometers are provided 431, 432.

For example, a first set of test conditions TC1 may be applied to the accelerometers 411 of the strapdown heading sensor. In response the first set of test conditions TC1, accelerometer compensation coefficients 421 are computed based on the raw data generated by the accelerometers 411 and reference data determined from a known reference source, such as a known acceleration applied to the accelerometers 411 or a reference sensor.

Further, a second set of test conditions TC2 may be applied to the magnetometers 412 of the strapdown heading sensor. In response the second set of test conditions TC2, magnetometer compensation coefficients 422 are computed based on the raw data generated by the magnetometers 412 and reference data determined from a known reference source. In some embodiments, the reference data may be calculated based on a geographical location of the magnetometers 412, a position of the magnetometers 412 relative to the Earth's magnetic field and/or a reference sensor.

Further, one or more of the following test conditions may be applied to the sensors of the uncalibrated strapdown sensor: varying a temperature of the uncalibrated strapdown sensor, varying an orientation of the uncalibrated strapdown sensor, varying magnetic fields applied to the uncalibrated strapdown sensor and altering a position of the uncalibrated strapdown heading sensor so as to affect a gravitational field applied to the uncalibrated strapdown sensor.

Further, during the factory calibration routine 415, the strapdown heading sensor may be configured to convert the compensated sensor data in the instrument frame relative to the strapdown heading sensor to compensated sensor data in the Earth's frame relative to the strapdown heading sensor. As a result, the strapdown heading sensor may output compensated sensor data in the Earth frame relative to the strapdown heading sensor.

Referring to FIG. 9, a platform calibrated strapdown heading sensor is provided as a result of the platform calibration routine 445. During the platform calibration routine 445, the output data of the strapdown heading sensor is compensated for errors in the apparatus frame of the target apparatus so as to provide a platform calibrated strapdown heading sensor.

For example, a third set of test conditions TC3 are provided to the strapdown heading sensor installed in or mounted to a target apparatus 441, and compensation coefficients 451 based on sensor data generated by the strapdown heading sensor and reference data determined from a known reference source are computed so that compensated sensor data is generated by the strapdown heading sensor that corresponds to a physical orientation of the target apparatus. In some embodiments, the reference data may be calculated based on a geographical location of the magnetometers, a position of the magnetometers relative to the Earth's magnetic field, a known acceleration applied to the accelerometers and/or a reference sensor. In this manner, a platform calibrated strapdown heading sensor 461 is provided, which is configured to generate data signals (e.g., data signals DS3 of FIG. 6) corresponding an attitude of the target apparatus.

FIG. 10 illustrates a towed array, in accordance with embodiments of the present inventive concepts. In this exemplary embodiment, a towed array 502 including a plurality of strapdown heading sensors 100 is shown attached to a surface ship 501. The strapdown heading sensors 100 are configured to determine an attitude of the portion of the towed array 502 to which they are coupled.

While the present inventive concepts have been particularly shown and described above with reference to exemplary embodiments thereof, it will be understood by those of ordinary skill in the art, that various changes in form and detail can be made without departing from the spirit and scope of the present inventive concepts described and defined by the following claims. 

What is claimed is:
 1. A strapdown heading sensor, comprising: an elongated housing; and a compass module at least partially positioned within an inner cavity of the elongated housing, the compass module including at least one solid state sensor, wherein the compass module is cantilevered within the inner cavity of the elongated housing.
 2. The strapdown heading sensor of claim 1, wherein the compass module is coupled to a surface of the inner cavity of the elongated housing.
 3. The strapdown heading sensor of claim 2, wherein a proximal end of the compass module is coupled to a proximal end of the elongated housing, and wherein a distal end of the compass module is suspended within a central region of the inner cavity of the elongated housing.
 4. The strapdown heading sensor of claim 2, wherein an end-cap of the compass module is coupled within a proximal end of the elongated housing.
 5. The strapdown heading sensor of claim 1, wherein the at least one solid state sensor comprises at least one magnetometer and at least one accelerometer.
 6. The strap down heading sensor of claim 5, wherein the at least one magnetometer comprises at least one selected magnetometer of a group consisting of: a uni-axial magnetometer, a bi-axial magnetometer and a tri-axial magnetometer.
 7. The strapdown heading sensor of claim 6, wherein the at least one accelerometer comprises at least one selected accelerometer from a group consisting of: a uni-axial accelerometer, a bi-axial accelerometer and a tri-axial magnetometer.
 8. A strapdown heading sensor, comprising: an elongated housing; and a compass module positioned within an inner cavity of the elongated housing, the compass module including at least one solid state sensor, wherein the compass module is passively isolated from shock or vibrations induced on an outer surface of the elongated housing.
 9. The strapdown heading sensor of claim 8, wherein the elongated housing includes a closed housing, and wherein the strapdown heading sensor further comprises an end-cap constructed and arranged to close a single opening of closed housing.
 10. The strapdown heading sensor of claim 8, wherein the elongated housing includes an opened housing, and wherein the strapdown heading sensor further comprises a first end-cap constructed and arranged to close a first opening of the opened housing and a second end-cap constructed and arranged to close a second opening of the opened housing.
 11. The strapdown heading sensor of claim 8, further comprising a damper positioned between the compass module and a surface of the inner cavity of the elongated housing.
 12. The strapdown heading sensor of claim 11, wherein the damper includes a first damper positioned about a proximal end of the compass module and a second damper positioned about a distal end of the compass module.
 13. The strapdown heading sensor of claim 12, wherein the damper further includes a first bumper positioned at the proximal end of the compass module and a second bumper positioned at the distal end of the compass module.
 14. A method of calibrating a strapdown heading sensor, comprising: compensating raw sensor data generated by sensors of an uncalibrated strapdown heading sensor to compensate for errors in an instrument frame of the strapdown heading sensor; providing the strapdown heading sensor in a target apparatus; and after providing the strapdown heading sensor in the target apparatus, compensating output data of the strapdown heading sensor to compensate for errors in an apparatus frame of the target apparatus relative to the instrument frame of the strapdown heading sensor, wherein the strapdown heading sensor comprises an elongated housing; and a compass module at least partially positioned within an inner cavity of the elongated housing, the compass module including at least one solid state sensor, wherein the compass module is cantilevered within the inner cavity of the elongated housing.
 15. The method of claim 14, wherein the errors in the instrument frame of the strap down heading sensor include at least one of: a misalignment of the sensors mounted within a housing of the strapdown heading sensor, an intra-sensor nonorthogonal error, an inter-sensor nonorthogonal error, a gain error, a bias error and hard/soft iron errors of the sensors of the strapdown heading sensor.
 16. The method of claim 14, wherein the errors in the apparatus frame of the strapdown heading sensor include at least one of: a misalignment of the sensors mounted within a housing of the strapdown heading sensor, a misalignment of the strapdown heading sensor mounted within the target apparatus, an intra-sensor nonorthogonal error, an inter-sensor nonorthogonal error, a gain error, a bias error and hard/soft iron errors of the sensors of the strapdown heading sensor.
 17. The method of claim 14, wherein compensating raw sensor data generated by sensors of an uncalibrated strapdown heading sensor includes: applying test conditions to the uncalibrated strapdown sensor; computing compensation coefficients based on raw sensor data generated by the uncalibrated strapdown sensor and reference data determined from a known reference source; and compensating the raw sensor data so that compensated sensor data generated by the strapdown heading sensor corresponds to a physical orientation of the strapdown heading sensor.
 18. The method of claim 17, wherein the known reference source is generated by a reference sensor.
 19. The method of claim 17, wherein applying test conditions to the uncalibrated strapdown sensor includes at least one of: varying a temperature of the uncalibrated strapdown sensor, varying an orientation of the uncalibrated strapdown sensor, varying magnetic fields applied to the uncalibrated strapdown sensor and altering a position of the uncalibrated strapdown heading sensor so as to affect a gravitational field applied to the uncalibrated strapdown sensor.
 20. The method of claim 17, further comprising: converting the compensated sensor data in the instrument frame of the strapdown heading sensor to compensated sensor data in the Earth's frame relative to the strapdown heading sensor; and outputting compensated sensor data in the Earth's frame relative to the strapdown heading sensor.
 21. The method of claim 14, wherein providing the strapdown heading sensor in a target apparatus introduces the errors in the apparatus frame relative to the strapdown heading sensor.
 22. The method of claim 14, wherein compensating output data of the strapdown heading sensor includes: applying test conditions to the strapdown sensor provided in the target apparatus; computing compensation coefficients based on sensor data generated by the strapdown sensor and reference data determined from a known reference source; and compensating the sensor data so that compensated sensor data generated by the strapdown heading sensor corresponds to a physical orientation of the target apparatus.
 23. The method of claim 22, wherein applying test conditions to the strapdown sensor provided in the target apparatus includes at least one of: varying a temperature of the strapdown sensor, varying an orientation of the uncalibrated strapdown sensor, varying magnetic fields applied to the uncalibrated strapdown sensor and altering a position of the uncalibrated strapdown heading sensor so as to affect a gravitational field applied to the uncalibrated strapdown sensor.
 24. The method of claim 22, wherein the known reference source is generated by a reference sensor. 